CN114136631B - High-temperature mechanical property measuring equipment for aeroengine vacuum bellows assembly - Google Patents
High-temperature mechanical property measuring equipment for aeroengine vacuum bellows assembly Download PDFInfo
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- CN114136631B CN114136631B CN202111230339.7A CN202111230339A CN114136631B CN 114136631 B CN114136631 B CN 114136631B CN 202111230339 A CN202111230339 A CN 202111230339A CN 114136631 B CN114136631 B CN 114136631B
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Abstract
The invention provides high-temperature mechanical property measuring equipment for an aeroengine vacuum bellows assembly, which comprises a low-temperature cavity for providing a working environment of a sensor, a high-temperature cavity for providing different target temperatures for the vacuum bellows assembly to be measured, and a sensing assembly for adjusting the working environments of the low-temperature cavity and the high-temperature cavity. The invention can make the vacuum bellows component generate certain expansion or compression through the change of the air pressure of the high-temperature cavity, and utilize the force measuring sensor to measure the force, and utilize the screw rod sliding table linear module and the force measuring sensor to measure the displacement. Thus, the air pressure-force-displacement relation curve of the vacuum bellows assembly at a certain high temperature is obtained, so that the travel of the high-altitude valve vacuum bellows of the aeroengine under the working conditions of different temperatures, different flying heights and the like can be accurately mastered.
Description
Technical Field
The invention relates to the field of aeroengines, in particular to high-temperature mechanical property measuring equipment for a vacuum bellows assembly of an aeroengine.
Background
At present, no related report of high-temperature mechanical property measuring equipment of the vacuum bellows component of the aeroengine exists at home and abroad.
The design of a vacuum constant temperature-based bellows component travel measurement control system in the journal 2016 of new technology and product of China is described in the section 7, which is used for controlling the travel inspection of the high-altitude valve bellows component of an aeroengine. Because of the absence of a force measuring device and the absence of a high-temperature atmospheric environment simulation cabin, the high-temperature mechanical property of the vacuum bellows assembly cannot be obtained.
Chinese patent application publication CN109632222a discloses a spring rate measuring apparatus and a measuring method thereof. The measuring equipment comprises a traction force acquisition system, a spring fixing table, a displacement control system, a driving system and a computer, is similar to a material testing machine, but is only limited to measuring the spring stiffness in a tensile state, and cannot be applied to a vacuum bellows assembly formed by superposing a plurality of vacuum bellows; due to the lack of a high-temperature atmospheric environment simulation cabin and a vacuum system, the vacuum bellows assembly can not be used for measuring the mechanical properties of the vacuum bellows assembly at different temperatures and different atmospheric environment pressures.
Disclosure of Invention
In order to solve the problems, the invention provides high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows assembly, which can accurately master the force-displacement relation of the vacuum bellows assembly at different flying heights and temperatures.
The invention aims to provide high-temperature mechanical property measuring equipment of an aeroengine vacuum bellows assembly, which comprises a low-temperature cavity for providing a working environment of a sensor, a high-temperature cavity for providing different target temperatures for the vacuum bellows assembly to be measured and a sensing assembly for adjusting the working environments of the low-temperature cavity and the high-temperature cavity,
the cryogenic chamber comprises:
the low-temperature cavity cylinder body is of a hollow structure, and a cooling medium is introduced into a hollow cavity of the low-temperature cavity cylinder body to reduce the ambient temperature in the low-temperature cavity;
and a measuring assembly: the measuring component is used for measuring the mechanical characteristics of the vacuum bellows component to be measured; the method comprises the steps of,
a connection assembly for transmitting mechanical properties of the bellows assembly to be measured to the measurement assembly for measurement,
the high temperature chamber includes:
the heat insulation cabin is used for insulating the high-temperature environment in the high-temperature cavity;
the heating ring is arranged in the heat insulation cabin and is used for providing the measured temperature of the vacuum bellows component to be measured;
the mounting assembly is arranged in the middle of the heating ring and used for fixing the vacuum bellows assembly to be tested; the method comprises the steps of,
and the disassembly assembly is arranged at the lower end of the installation assembly and is used for replacing the vacuum bellows assembly to be tested.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the measuring component comprises a force transducer for measuring the mechanical property transmitted by the connecting component, the force transducer is arranged on a sliding block of a linear module of a screw rod sliding table through an adapter, the linear module of the screw rod sliding table is fixed on the inner wall of the low-temperature cavity cylinder body, and a screw rod of the linear module of the screw rod sliding table is driven to rotate through a servo motor to drive the sliding block to move.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the connecting component comprises a ceramic guide rod, and the lower end of the ceramic guide rod is disc-shaped.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention also has the characteristic that the heat insulation cabin is made of high-temperature-resistant polyurethane plates.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the heating ring and the high-temperature cavity cylinder body are respectively provided with an observation window and a light transmission window along the circumferential direction, and the observation window and the light transmission window are spaced by 90 degrees along the circumferential direction.
The invention provides high-temperature mechanical property measuring equipment of an aeroengine vacuum bellows component, which is characterized in that the mounting component comprises:
the guide cylinder is in small clearance fit with the vacuum bellows assembly to be tested and is used for coaxially guiding the vacuum bellows assembly to be tested;
the adjusting pad is arranged at the lower end of the vacuum bellows assembly to be measured and is used for adjusting the installation height of the vacuum bellows assembly to be measured; and
and the heat insulation plate is arranged below the adjusting pad and is used for insulating the temperature of the vacuum bellows component to be tested.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the guide cylinder is axially provided with grid bars, and the guide cylinder is fixed on a cavity bottom plate of the high-temperature cavity.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the dismounting component comprises a metal gland controlled by a hinge, and a small red copper gasket is arranged between the metal gland and the cylinder body of the high-temperature cavity.
The high-temperature mechanical property measuring equipment for the vacuum bellows component of the aeroengine is characterized in that the sensing component comprises a first temperature sensor for measuring the temperature of a low-temperature cavity, a second temperature sensor for measuring the temperature of the vacuum bellows component to be measured, an absolute pressure transmitter for measuring the pressure of gas in the high-temperature cavity, an interface for introducing compressed gas into the low-temperature cavity, a cooling medium inlet and a cooling medium outlet for introducing cooling medium into the hollow cavity and a vacuum pump connected to the high-temperature cavity.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the absolute pressure transmitter is arranged on the outer side of the low-temperature cavity cylinder body, and the absolute pressure transmitter measures the gas pressure in the high-temperature cavity through the stainless steel capillary pressure guiding pipe extending into the high-temperature cavity.
The high-temperature mechanical property measuring equipment for the aeroengine vacuum bellows component provided by the invention is further characterized in that the low-temperature cavity is provided with an organic glass cover, and the organic glass cover is sealed with the low-temperature cavity cylinder body through a fluororubber sealing ring; and a sealing red copper gasket is arranged between the low-temperature cavity and the high-temperature cavity.
Compared with the prior art, the invention has the following beneficial effects
The device comprises a low-temperature cavity and a high-temperature cavity; the low-temperature cavity provides working environments for components such as a force transducer, and the high-temperature cavity provides high-temperature environments with different target temperatures for a vacuum bellows assembly of a measured object.
The invention can make the vacuum bellows component generate certain expansion or compression through the change of the air pressure of the high-temperature cavity, and utilize the force measuring sensor to measure the force, and utilize the screw rod sliding table linear module and the force measuring sensor to measure the displacement. Thus, the air pressure-force-displacement relation curve of the vacuum bellows assembly at a certain high temperature is obtained, so that the travel of the high-altitude valve vacuum bellows of the aeroengine under the working conditions of different temperatures, different flying heights and the like can be accurately mastered.
The K-type armoured thermocouple for measuring the temperature of the vacuum bellows component has the accuracy of 1 level, the accuracy of an absolute pressure transmitter for measuring the air pressure of the high-temperature cavity is +/-0.5%, the accuracy of the force transducer is +/-0.1%, the linear module of the screw rod sliding table can record displacement to be accurate to 0.02mm, and the measurement result is accurate.
Description of the drawings:
in order to more clearly illustrate the technical solutions of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a high temperature mechanical property measurement device for an aeroengine vacuum bellows assembly provided by the invention;
figure 2 is a working logic diagram of the high-temperature mechanical property measuring equipment of the vacuum bellows component of the aeroengine,
the device comprises a 1-low temperature cavity, a 2-organic glass cover, a 3-fluororubber sealing ring, a 4-low temperature cavity cylinder, a 5-Pt100 platinum resistance temperature sensor, a 6-K type armored thermocouple temperature sensor, a 7-absolute pressure transmitter, an 8-stop valve, a 9-stainless steel capillary pressure guiding tube, a 10-servo motor, an 11-screw sliding table linear module, a 12-mounting seat, a 13-adapter, a 14-force transducer, a 15-ceramic guide rod, a 16-large red copper gasket, a 17-high temperature cavity, a 18-high temperature cavity cylinder, a 19-heat insulation cabin, a 20-heating ring, a 21-guide cylinder, a 22-vacuum bellows component to be tested, a 23-small red copper gasket, a 24-adjusting pad, a 25-heat insulation disc, a 26-metal gland, a 27-hinge, a 28-water cooler, a 29-vacuum pump, a 30-absolute pressure gauge and a 31-electromagnetic valve.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement of the purposes and the effects of the present invention easy to understand, the following embodiments specifically describe the measurement device provided by the present invention with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
As shown in fig. 1-2, an embodiment of the present invention provides a measurement device for high temperature mechanical properties of an aeroengine vacuum bellows assembly, the measurement device including a low temperature chamber 1 for providing a working environment of a sensor, a high temperature chamber 17 for providing different target temperatures for the vacuum bellows assembly 22 to be measured, and a sensing assembly for adjusting the working environments of the low temperature chamber 1 and the high temperature chamber 17, the low temperature chamber 1 including: a low-temperature cavity cylinder body 4 with a hollow structure, wherein a cooling medium is introduced into a hollow cavity of the low-temperature cavity cylinder body 4 for reducing the environmental temperature in the low-temperature cavity 1; and a measuring assembly: the measuring assembly is used for measuring the mechanical property of the vacuum bellows assembly 22 to be measured; and a connection assembly for transferring mechanical properties of the bellows assembly 22 to be measured to the measurement assembly for measurement; the high temperature chamber 17 includes: the heat insulation cabin 19 is used for insulating the high-temperature environment in the high-temperature cavity 17; a heating ring 20 arranged in the heat insulation cabin 19 for providing a measured temperature of the vacuum bellows assembly 22 to be measured; the mounting assembly is arranged in the middle of the heating ring 20 and is used for fixing the vacuum bellows assembly 22 to be tested; and a disassembly assembly is arranged at the lower end of the installation assembly and is used for replacing the vacuum bellows assembly 22 to be tested.
The low-temperature cavity cylinder 4 is of a welded hollow structure, and can circulate cooling water to ensure that the ambient temperature in the low-temperature cavity 1 is no more than 40 ℃ so as to ensure that electronic components and wires thereof in the low-temperature cavity 1 work normally, and also can be filled with normal-temperature compressed air, and flows into the high-temperature cavity 17 through a ceramic guide rod 15 and a bottom plate hole gap of the low-temperature cavity cylinder 4 and a top plate hole gap of the high-temperature resistant polyurethane heat insulation cabin 19 so as to realize mixing with high-temperature gas in the high-temperature cavity 17, so that the vacuum bellows assembly 22 tends to be stable at a certain high temperature; in the vacuumizing process, high-temperature air in the high-temperature cavity cylinder 18 flows through the water cooler 28 firstly, and is pumped by the vacuum pump 29 and then is exhausted, so that the vacuum pump 29 is prevented from being damaged due to high temperature; when the force is measured, the slide block in the screw rod sliding table linear module 11 is ensured to be static, the vacuum bellows assembly 22 expands in the process of vacuumizing the high-temperature cavity 17 from normal pressure, the reading of the vacuum bellows assembly is gradually increased by transmitting the force to the force transducer 14 through the ceramic guide rod 15, the normally open electromagnetic valve 31 needs to be powered off in the process of recovering the high-temperature cavity 17 from vacuum normal pressure, normal-temperature compressed air is led into the high-temperature cavity 17, and meanwhile, the electric heating ring 20 continuously works to ensure that the vacuum bellows assembly 22 is in a target temperature range, the vacuum bellows assembly 22 contracts in the process, and the reading of the force transducer 14 is reduced; when the displacement is measured, the servo motor 10 works, as shown in fig. 2, the upper surface of the vacuum bellows assembly 22 is tracked by a slide block of the screw rod sliding table linear module 11, the force transducer 14 and the ceramic guide rod 15 through a PLC program, so that the displacement data of the vacuum bellows assembly 22 are read; to sum up, the force and displacement data of the vacuum bellows assembly 22 in the process of changing along with the air pressure at the target temperature can be recorded, namely, the high-temperature mechanical property measurement of the vacuum bellows assembly 22 is realized.
In some embodiments, the measuring assembly includes a force transducer 14 for measuring the mechanical property transferred by the connecting assembly, the force transducer 14 is mounted on the adapter 13 through an M8 screw, the adapter 13 is mounted on the slider of the screw sliding table linear module 11, the screw sliding table linear module 11 is fixed on the inner wall of the low temperature cavity cylinder 4 through the mounting seat 12, and the screw of the screw sliding table linear module 11 drives rotation through the servo motor 10 to drive the movement of the slider.
In some embodiments, the connecting assembly includes a ceramic guide rod 15, where the lower end of the ceramic guide rod 15 is disc-shaped, and the upper end is an M8 external thread, and is fixedly connected to the lower end of the load cell 14. The ceramic guide rod 15 is made of zirconia or silica. The disc-shaped ceramic guide rod 15 can have a larger contact area with the upper surface of the vacuum bellows assembly 22 to be tested.
In some embodiments, the thermal insulation compartment 19 is made of a high temperature resistant polyurethane board.
In some embodiments, the heating ring and the high temperature chamber cylinder 18 are provided with a viewing window and a light-transmitting window respectively along the circumferential direction, and the viewing window and the light-transmitting window are spaced by 90 ° along the circumferential direction. The guide cylinder 21 is densely grooved along the axial direction, and the observation window of the high-temperature cavity cylinder 18 is provided with hollow toughened glass, so that the visualization of the expansion or contraction process of the vacuum bellows assembly 22 can be realized. The heating coil, i.e., the electrical heating coil 20, has a power of 2kW, which allows the evacuated bellows assembly to be heated to 500 c.
In some embodiments, the mounting assembly comprises: the guide cylinder 21 is in small clearance fit with the vacuum bellows assembly 22 to be tested, and is used for coaxially guiding the vacuum bellows assembly 22 to be tested; an adjusting pad 24, disposed at the lower end of the vacuum bellows assembly 22 to be measured, for adjusting the installation height of the vacuum bellows assembly 22 to be measured; and a heat insulation plate 25, disposed below the adjusting pad 24, for insulating the temperature of the vacuum bellows assembly 22 to be measured.
In some embodiments, the guide cylinder 21 is axially provided with grid bars, and the guide cylinder 21 is fixed on a cavity bottom plate of the high-temperature cavity 17. The guide cylinder 21 is provided with 3 holes circumferentially and uniformly distributed along the mounting edge and is fastened on the bottom plate of the high-temperature cavity cylinder 18 through screws.
In some embodiments, the disassembly assembly comprises a metal gland 26 controlled by a hinge 27, and a small red copper gasket 23 is arranged between the metal gland 26 and the cylinder of the high temperature chamber 17. The stainless steel gland 26 may be opened or closed to enable replacement of the subject vacuum bellows assembly 22. The small red copper gasket 23 seals between the high temperature chamber cylinder 18 and the stainless steel gland 26.
In some embodiments, the sensing assembly includes a first temperature sensor 5 for measuring the temperature of the low temperature chamber 1, a second temperature sensor 6 for measuring the temperature of the bellows assembly 22 to be measured, an absolute pressure transmitter 7 for measuring the pressure of the gas in the high temperature chamber 17, an interface for introducing compressed gas into the low temperature chamber 1, a cooling medium inlet and a cooling medium outlet for introducing cooling medium into the hollow chamber, and a vacuum pump connected to the high temperature chamber. The second temperature sensor 6 is a K-type armored thermocouple temperature sensor, the probe of the second temperature sensor 6 is welded on the outer wall of the guide cylinder 21 through a stainless steel sheet, the lead wire of the second temperature sensor 6 is led out through holes at the top cover of the high-temperature-resistant polyurethane heat insulation cabin 19, the bottom plate, the side wall and other positions of the low-temperature cavity cylinder body 4, and after the lead wire is led out, the gaps of the small holes are sealed through high-temperature glue.
In some embodiments, the absolute pressure transmitter 7 is disposed outside the low temperature chamber cylinder 4, and the absolute pressure transmitter 7 measures the gas pressure in the high temperature chamber 17 through a stainless steel capillary pressure guiding tube 9 extending into the high temperature chamber 17. One end of the stainless steel capillary pressure guiding pipe 9 extends into the high temperature cavity 17, the other end is led out through holes at the top cover of the high temperature resistant polyurethane heat insulation cabin 19, the bottom plate, the side wall and other positions of the low temperature cavity cylinder 4, is connected to the absolute pressure transmitter 7, and seals the gaps of the small holes by high temperature glue.
In some embodiments, the low-temperature chamber 1 is provided with a plexiglass cover 2, and the plexiglass cover 2 and the low-temperature chamber cylinder 4 are sealed by a fluororubber sealing ring 3; a sealing copper washer 16 is arranged between the low temperature chamber 1 and the high temperature chamber 17.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (8)
1. A measuring device for high-temperature mechanical properties of an aeroengine vacuum bellows assembly is characterized by comprising a low-temperature cavity for providing a working environment of a sensor, a high-temperature cavity for providing different target temperatures for the vacuum bellows assembly to be measured and a sensing assembly for adjusting the working environments of the low-temperature cavity and the high-temperature cavity,
the cryogenic chamber comprises:
the low-temperature cavity cylinder body is of a hollow structure, and a cooling medium is introduced into a hollow cavity of the low-temperature cavity cylinder body to reduce the ambient temperature in the low-temperature cavity;
and a measuring assembly: the measuring component is used for measuring the mechanical characteristics of the vacuum bellows component to be measured; the method comprises the steps of,
a connection assembly for transmitting mechanical properties of the bellows assembly to be measured to the measurement assembly for measurement,
the high temperature chamber includes:
the heat insulation cabin is used for insulating the high-temperature environment in the high-temperature cavity;
the heating ring is arranged in the heat insulation cabin and is used for providing the measured temperature of the vacuum bellows component to be measured;
the mounting assembly is arranged in the middle of the heating ring and used for fixing the vacuum bellows assembly to be tested; the method comprises the steps of,
the disassembly component is arranged at the lower end of the installation component and is used for replacing the vacuum bellows component to be tested,
the measuring component comprises a force transducer for measuring the mechanical property transmitted by the connecting component, the force transducer is arranged on a slide block of a screw rod sliding table linear module through an adapter, the screw rod sliding table linear module is fixed on the inner wall of the low-temperature cavity cylinder body, a screw rod of the screw rod sliding table linear module is driven to rotate through a servo motor to drive the slide block to move,
the connecting component comprises a ceramic guide rod, the lower end of the ceramic guide rod is disc-shaped,
the sensing assembly comprises a first temperature sensor for measuring the temperature of the low-temperature cavity, a second temperature sensor for measuring the temperature of the vacuum bellows assembly to be measured, an absolute pressure transmitter for measuring the pressure of gas in the high-temperature cavity, an interface for introducing compressed gas into the low-temperature cavity, a cooling medium inlet and a cooling medium outlet for introducing cooling medium into the hollow cavity, and a vacuum pump connected to the high-temperature cavity.
2. The apparatus for measuring high temperature mechanical properties of an aircraft engine evacuated bellows assembly of claim 1, wherein the insulation capsule is made of a high temperature resistant polyurethane sheet material.
3. The apparatus of claim 1, wherein the heating ring and the high temperature chamber cylinder are provided with a viewing window and a light transmission window respectively along a circumferential direction, and the viewing window and the light transmission window are spaced by 90 ° along the circumferential direction.
4. The aero-engine evacuated capsule assembly high temperature mechanical property measurement apparatus of claim 1, wherein the mounting assembly comprises:
the guide cylinder is in small clearance fit with the vacuum bellows assembly to be tested and is used for coaxially guiding the vacuum bellows assembly to be tested;
the adjusting pad is arranged at the lower end of the vacuum bellows assembly to be measured and is used for adjusting the installation height of the vacuum bellows assembly to be measured; and
and the heat insulation plate is arranged below the adjusting pad and is used for insulating the temperature of the vacuum bellows component to be tested.
5. The apparatus of claim 4, wherein the guide tube is axially provided with grid bars, and the guide tube is fixed on a cavity bottom plate of the high temperature cavity.
6. The apparatus of claim 1, wherein the disassembly assembly comprises a metal gland controlled by a hinge, and a small red copper gasket is disposed between the metal gland and the barrel of the high temperature chamber.
7. The apparatus of claim 1, wherein the absolute pressure transmitter is disposed outside the low temperature chamber cylinder and measures the gas pressure in the high temperature chamber through a stainless steel capillary pressure tube extending into the high temperature chamber.
8. The aeroengine vacuum bellows assembly high temperature mechanical property measurement apparatus of claim 1, wherein the low temperature chamber is provided with an organic glass cover, and the organic glass cover and the low temperature chamber cylinder are sealed by a fluororubber sealing ring; and a sealing red copper gasket is arranged between the low-temperature cavity and the high-temperature cavity.
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